Aeroplane radiator



1927' H. c. MUMMERT ET AL,

AEROPLANE RADIATOR Filed NOV. 29, 1922 T IG. INVENTOR5 HARVEY C. Mummzam, JOJEPHF. MEADE.

B Y Q 6 g [-3 flTTORNE Y.

Patented 11, 1927.

UNITED STATES PATENT OFFICE."

mm o. mummnnr, or norms, AND JOSEPH F. MEADE, or rnnnron'r, NEW

YORK, ASSIGNORS, BY MESNE AS SIGNMENTS, TO CURTISS AEROILANE AND MOTOR COMPANY, INC., OF GARDEN CITY, NEW YORK, A CORPORATION OF NEW YORK.

AEnorLANn nanrn'ron.

Application filed November Our invention relates to aeroplane radian tors and more particularly to improvements in wing radiators of the skin or surface type, i. e., a type recently developed by the I Gurtiss Aeroplane & Motor Corporation,

and disclosed in its original form in application Serial No. 470,186, fiI'ed May 16th, 1921.

An object of the invention is to construct W the radiator in parts or sections that the separate parts or sections may be separately assembled or removed to the end that installation, repair, and replacement, can be easily and quickly accomplished.

A further object of the'invention is the construction of the radiator parts or sec- 5 tions in such a manner that one of said parts or sections is adapted to provide an outer covering for a given portion. ofthe lid to wing or aerofoil in connection with which it is used, whereas another section or other sections are adapted to provide an outer covering for the remaining part or portion of said win or aerofoil said radiator parts or sections eing separately removable and so organized as to collectively define a hol-' wing or aerofoil as to provide the neces W sarg cooling surface.

ther ob ects of the invention, such for instance as "the specific disposition of theheader sections, the arrangement of the inlet and outlet water passages respectively W to and from the headers, the header forma-- tion in cross section, etc, will be hereinafter more fully explained.

In the drawings, wherein likereference characters designate like or corresponding W parts:---

Figure 1 is a plan view of a radiator constructed in accordance with the teachings of the present invention;

29, 1922. Serial No. 604,076.

Figure 2 is an enlarged transverse sec- .Figure 3 is a detail sectional view of a portion of the forward header showing the manner in which the headerv sections are joined; and,

' Figure 4 is a detail sectional view of the rear header showing the manner in which the outlet water passage is fastened in place. As'explained in the original application above referred to, wing radiators of the skin or surface type are especially desirable in view of the lack of head resistance which radiators. of this particular type offer to forward flight. In the embodiment of the invention selected for illustration the radiator comprises separate radiator sections 10 placed edge to edge both on the to surface and on the" under surface of t e wing. Thus organized, it is apparent that the wing, designated at 11, rovides thenecessary radiator support. t its forward end the radiator is provided with a forward header 12 andat its rear end is provided with a rear header 13, the former being so related. to the wing 11 as to constitute the nose portion thereof, and the latter 50 related to the wing 11 as to constitute the trailing edge portion thereof. Both head'- ers 12 and 1% are of gradually decreasing cross sectional area from end to end, the forward header 12 at its larger end being provided with an inlet water passageway 14land the header 13 at its larger end being provided with anoutlet water passageway 15. Such difi'erence in cross sectional area of the radiator headers is instrumental in obtaining a more uniform distribution of the cooling agent in its circulation through the various radiator parts;

The forward header 12 of the radiator comprises separate header sections 16 and 17, whereas the rear header '13 comprises separate header sections 18 and 19.- Each header section is formed of sheet metal bent as indicated in Figure 2 to prgvide a plurality of securing flanges 20, the flanges 20 of the header sections 16 and 17 being adapted to overlap, as are also the flan es 20 of the header sections 18 and 19. 'lectively the flanges20 provide a means for fastening the header sections, together,

7 sections 10 which bear on the under surface of the wing interconnect the forward header sectlon 17 with the rear header section 18, and since the interconnecting portions are in each instance integral with the header sec-" tions which they connect, obviously. the radiator considered inits entirety, maybe said to comprise separate radiator parts.

The headers 12 and '13 are open ended at their larger ends and provided with flanges 23 for the attachment of the water pipes 14 and 15, said pipes being likewise anged as indicated at 24 and riveted as at 25 to the flanges 23 which they abut. Be-

tween the flanges 23 and 24 suitable packing 26 is interposed. ,1 It is obvious from the foregoing that the radiator parts are each so organized as to tions' .16

provide an outer covering for a portion only of the It is further evident that the radiator {parts may be separately removed and replaced without correspondingly reor in any way effecting the remainin radiate partor parts. 'If desired, instea nnecting the header sections 16 and 'cated in Figure 2 the header secand 18 may be interconnected, in which 'ieventl the header sections 17- and 19 s'hofild h'e interconnected instead of the header saiqnsiz and 18 as shown. Preferably i urface or interconnecting porconstructed in accordance with ffltofore explained in applicae. While we have described our invention in detail "in fit's'pre'sent preferred embodiment,

it will bejob'vlous to those skilled in the art after Lunderstandin 1 our invention, that various changes an modifications may be ,made therein without departing from the spirit -or'scopelthereof. We aim in the appended claims to -cover all such modificatlons and changes].

f '1. aeroplane radiator comprising separate headers, each header. in turn comprising separa te substantially parallel header sections, a connecting portion between one header section of 'each header, and a connecting portion between the other header section of each header, the connecting portions, in each instance, being separately formed and so organized as to jointly provide the radiator cooling surface. 7

2. An aeroplane radiator comprising separate headers, each header in turn comprls ing separate substantially parallel header sections, a connecting portion between one header section of each header, a connecting portion between the otherheader section of each header, the connecting portions in"each instance being separately formed and so organized as to jointly provide the radiator cooling surface, an inlet water passage common to the header sections of one of said headers, and an outlet water passage common to the header sections of the other of said headers.

3. An aeroplane radiator comprising longitudinally divided headers of gradually decreasing cross sectional area from end to end, connections between the divided headers so constructed as to provide the necessary cooling surface, an inlet water passage common to the divisions comprising one .of said headers,":ind an outlet water passage common to the divisions comprising the .otherof said headers, said water passages A. An aeroplane radiator comprising, in combination with an aerofoil, separate rad1-.

ator headers, each header comprising separate substantially parallel header sections arranged to extend longitudinally of the aerofoil, a connecting "portion between one header section of each header arranged to provide an outer covering for a portion, at

least, of the top surface of the aerofoil, a

connecting portion between the other header sections of each header arranged to provide an outer covering for a portion, at least, of

the under surfaceof the aerofoil, and said connecting portions jointly providing-the radiator cooling surface.

5. An aeroplane radiator comprising, in

combination with an aerofoil, a radiator section comprising separate header portions and a connecting portion, said connecting portion being fastened in place upon the aerofoil to provide an outer covering for a portion, at least, of the top surface thereof, a second radiator section comprising separate header portions and aconnecting portion' in which the latter connectin portion is fastened in place uponthe .aero oil'to provide therefor an outer covering for a'portion,

at least, of the under surface of the aerofoil,

the header portions of each radiator sectionbeing extended lengthwise the aerofoil and contlguous, to the corresponding header portions of said two radiator sections, and an outlet water assagecommon to the two remaining eader-portions thereof.

In testimony whereof they hereunto aflix their signatures.

' HARVEY o. MUMMERT. JOSEPH F, MEADE an inlet water passage'common 

